CN107757878A - A kind of flight control system out-of-balance force balancing device - Google Patents
A kind of flight control system out-of-balance force balancing device Download PDFInfo
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- CN107757878A CN107757878A CN201710816804.2A CN201710816804A CN107757878A CN 107757878 A CN107757878 A CN 107757878A CN 201710816804 A CN201710816804 A CN 201710816804A CN 107757878 A CN107757878 A CN 107757878A
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- balance force
- torque tube
- rocking arm
- balancing device
- weight
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Abstract
The invention discloses a kind of flight control system out-of-balance force balancing device.The device is made up of sectional wheel (1), rocking arm (2), torque tube (3), (4) No. two bearings (5) of No.1 bearing and adjustable pouring weight (6).Flexible control linear system (7) is connected with sectional wheel (1), and rigid control linear system (8) is be hinged with rocking arm (2).The crosslinking of the arrangement of rigid rod and linkage and Ren Gan mechanisms, the steady, automatic pilot of control increasing etc. in steerable system is offset by counterweight, " out-of-balance force " of introducing, improves man-machine efficacy, increases handling comfort, improve flight quality.The present invention is simple in construction, and mounting and adjusting is convenient, shortens the steerable system general assembly adjustment cycle.
Description
Technical field
The present invention relates to aircraft flight control technology field, is on out-of-balance force in flight control system specifically
The device of trim.
Background technology
Aircraft handling linear system is divided into flexible control and rigid control according to its used conveying member.Flexible control linear system
Have the advantages that in light weight, cost is low, linear system arrangement is convenient, rigid control linear system has that good rigidity, maintainability be good, system friction
The advantages that power is small.The aircraft of early stage uses flexible control more, and with the development of steerable system, current all kinds of aircrafts are more using soft or hard
Hybrid manipulation, leading portion, which manipulates, mostly uses flexible control, and linear system is all to use rigid control, traditional connection after booster
Mode is directly to dock, and is exactly to be connected by sectional wheel with rocking arm.The arrangement and control wire of rigid rod in existing steerable system
" out-of-balance force " that the crosslinking of system and Ren Gan mechanisms, the steady, automatic pilot of control increasing etc. introduces, causes left and right, front and rear steering force
Especially startup power is inconsistent, and the startup power of a direction is bigger than normal, and startup power is often exceeded when steerable system general assembly adjusts, and causes
Adjustment is difficult, influences manufacturing schedule；Other steerable system can make man-machine efficacy be deteriorated in the presence of " out-of-balance force ", influence flight product
Matter.
The content of the invention
Goal of the invention：The present invention provides a kind of flight control system out-of-balance force balancing device, reduces general assembly and adjusts repeatedly
Full employment, significantly shorten the system call interception cycle, increase handling comfort, improve flight quality.
Technical scheme：A kind of flight control system is with out-of-balance force balancing device by sectional wheel (1), rocking arm (2), torque tube
(3), No.1 bearing (4), No. two bearings (5) and adjustable pouring weight (6) composition, No.1 bearing (4) and No. two bearings (5) and structure
Reinforcing frame is connected, and torque tube (3) is connected with No.1 bearing (4), No. two bearings (5), torque tube (3) can around own axis,
Sectional wheel (1), rocking arm (2), adjustable pouring weight (6) and torque tube (3) are connected, and sectional wheel (1) connects with flexible control linear system (7)
Connect, rocking arm (2) is be hinged with rigid control linear system (8), transmits control command；
Further, adjustable pouring weight (6) is by lid (9), balancing weight (10), support (11), grooved metal gasket (12) and spiral shell
Bolt (13) forms, and slides the torque arm length for changing counterweight to torque tube (3) axis in support (11) by balancing weight (10)；
Further, the weight of the balancing weight (10) in adjustable pouring weight (6) can be according to the steerable system of different aircrafts
Trim demand is configured.
Advantageous effects
Compared with prior art, the beneficial effects of the invention are as follows：
Out-of-balance force that can be in trim control system while 1 present invention connection soft and hard type linkage, improves man-machine work(
Effect, increase handling comfort, improve flight quality.
The counterweight of " out-of-balance force " that 2 trim linear system arrangements of the present invention introduce is adjustable, can make up production and installation process
Individual difference in same model caused by middle tolerance build-up, versatility are good.
3 present apparatus features are simple in construction, and mounting and adjusting is convenient, significantly shorten the system call interception cycle.
Brief description of the drawings
Fig. 1 is flight control system out-of-balance force balancing device front view,
Fig. 2 is flight control system out-of-balance force balancing device side view,
Fig. 3 is adjustable pouring weight schematic diagram；
Wherein：1. the adjustable pouring weight 7. of 2. rocking arm of sectional wheel, 3. torque tube, 4. No.1 bearing, 5. No. two bearings 6. is soft
The rigid control linear system of formula linkage 8..
Embodiment
The present invention is described in further detail with embodiment below in conjunction with the accompanying drawings：
Referring to accompanying drawing 1 and the flight control system of accompanying drawing 2 with out-of-balance force balancing device by sectional wheel (1), rocking arm (2), torsion
Solenoid (3), No.1 bearing (4), No. two bearings (5) and adjustable pouring weight (6) composition.Under normal circumstances, deployment scenarios are shown in Fig. 1,
Pilot guidance instruction is delivered on sectional wheel (1) by leading portion flexible control linear system (7), then is delivered to by torque tube (3)
Rocking arm (2), endpiece rigid control linear system (8) is finally output to, makes control surface deflection；Produced according to linkage arrangement " uneven
The situation of power ", balancing weight and control command transformational relation can be commonly used another deployment scenarios and seen Fig. 2, pilot with flexible arrangement
Control command is delivered on rocking arm (2) by leading portion rigid control linear system (8), then is delivered to sectional wheel by torque tube (3)
(1) flexible control linear system (7), is output to, endpiece rigid control linear system is eventually transferred into, makes control surface deflection.
Referring to the adjustable pouring weight (6) of accompanying drawing 3 by lid (9), balancing weight (10), support (11), grooved metal gasket (12) and spiral shell
Bolt (13) forms.Balancing weight (10) material selection lead, space occupancy volume is few, and support (11) and grooved metal gasket (12) are provided with tooth form
Face, support (11) and lid (9) are provided with guide groove.Balancing weight (10) is fixed on support by bolt (13) and grooved metal gasket (12)
(11) on, bolt (13) can slide in the guide groove on support (11) and lid (9), on grooved metal gasket (12) and support (11)
Toothed surface is engaged, and is connected reliably after ensureing installation, is prevented balancing weight from being slided using process, changes system mode.
During same model aircraft general assembly, according to the individual difference situation of system installation, by adjusting balancing weight
(10) center of gravity changes the size of trim torque, reaches the imbalance of trim control system to the distance of torque tube (3) axis
The purpose of power.
For different model aircraft, the weight of the balancing weight (10) in adjustable pouring weight (6) can be according to the behaviour of different aircrafts
The trim demand of vertical system is configured, then adjusts the size of trim torque, reaches the mesh of the out-of-balance force of trim control system
's.
Claims (3)
- A kind of 1. flight control system out-of-balance force balancing device, by sectional wheel (1), rocking arm (2), torque tube (3), No.1 branch Seat (4), No. two bearings (5) and adjustable pouring weight (6) composition, it is characterised in that：No.1 bearing (4) and No. two bearings (5) and knot Structure reinforcing frame is connected, and torque tube (3) is connected with No.1 bearing (4), No. two bearings (5), and torque tube (3) can turn around own axes Dynamic, sectional wheel (1), rocking arm (2), adjustable pouring weight (6) and torque tube (3) are connected, sectional wheel (1) and flexible control linear system (7) Connection, rocking arm (2) is be hinged with rigid control linear system (8), transmits control command.
- A kind of 2. flight control system out-of-balance force balancing device according to claim 1, it is characterised in that：It is described can Allotment pouring weight (6) is made up of lid (9), balancing weight (10), support (11), grooved metal gasket (12) and bolt (13), passes through counterweight Block (10) slides the torque arm length for changing counterweight to torque tube (3) axis in support (11).
- A kind of 3. flight control system out-of-balance force balancing device according to claim 1, it is characterised in that：It is described can The weight of balancing weight (10) in allotment pouring weight (6) can be set.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710816804.2A CN107757878B (en) | 2017-09-12 | 2017-09-12 | Plane control system is with balanced device of uneven power |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710816804.2A CN107757878B (en) | 2017-09-12 | 2017-09-12 | Plane control system is with balanced device of uneven power |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107757878A true CN107757878A (en) | 2018-03-06 |
| CN107757878B CN107757878B (en) | 2020-04-28 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710816804.2A Active CN107757878B (en) | 2017-09-12 | 2017-09-12 | Plane control system is with balanced device of uneven power |
Country Status (1)
| Country | Link |
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| CN (1) | CN107757878B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109436302A (en) * | 2018-10-12 | 2019-03-08 | 陕西飞机工业（集团）有限公司 | A kind of transmission mechanism between cable wire and pull rod |
| CN112880917A (en) * | 2021-01-13 | 2021-06-01 | 万丰飞机工业有限公司 | Static balancing tool and measuring method for airplane control surface |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202686756U (en) * | 2012-03-09 | 2013-01-23 | 陕西飞机工业（集团）有限公司 | Control surface deflection angle limiting device |
| CN204822058U (en) * | 2015-04-29 | 2015-12-02 | 陕西飞机工业（集团）有限公司 | Balancing unit among aircraft control system |
| US20160152323A1 (en) * | 2014-10-13 | 2016-06-02 | Gulfstream Aerospace Corporation | Aircraft, systems, and methods for trim control in fly-by-wire aircraft systems |
| CN106143875A (en) * | 2016-09-23 | 2016-11-23 | 江西洪都航空工业集团有限责任公司 | A kind of hybrid steerable system of light aerocraft elevator |
-
2017
- 2017-09-12 CN CN201710816804.2A patent/CN107757878B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202686756U (en) * | 2012-03-09 | 2013-01-23 | 陕西飞机工业（集团）有限公司 | Control surface deflection angle limiting device |
| US20160152323A1 (en) * | 2014-10-13 | 2016-06-02 | Gulfstream Aerospace Corporation | Aircraft, systems, and methods for trim control in fly-by-wire aircraft systems |
| CN204822058U (en) * | 2015-04-29 | 2015-12-02 | 陕西飞机工业（集团）有限公司 | Balancing unit among aircraft control system |
| CN106143875A (en) * | 2016-09-23 | 2016-11-23 | 江西洪都航空工业集团有限责任公司 | A kind of hybrid steerable system of light aerocraft elevator |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109436302A (en) * | 2018-10-12 | 2019-03-08 | 陕西飞机工业（集团）有限公司 | A kind of transmission mechanism between cable wire and pull rod |
| CN112880917A (en) * | 2021-01-13 | 2021-06-01 | 万丰飞机工业有限公司 | Static balancing tool and measuring method for airplane control surface |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107757878B (en) | 2020-04-28 |
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| CP03 | Change of name, title or address |
Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: Box 34, Hanzhong City, Shaanxi Province, 723213 Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |
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